Rotor position determination system with hall-effect sensors

• US 8,955,792 B2
• Filed: 08/31/2012
• Issued: 02/17/2015
• Est. Priority Date: 08/31/2012
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Schank, Troy C.
• Primary Examiner(s): Bonzell, Philip J
• Application Number:
  US13/601,077
• Publication Number:
  US 20140061369A1
• Time in Patent Office: 900 Days
• Field of Search: 244/17.13, 244/17.25, 416/1, 416/3, 416/131, 416/133
• US Class Current: 244/17.13
• CPC Class Codes: B64C 27/008 Rotors tracking or balancing devices
• CPC Class Codes: B64C 27/35 having elastomeric joints
• CPC Class Codes: G01D 5/145 influenced by the relative movement between the Hall device and magnetic fields see G01R33/06

Abstract

According to one embodiment, a rotor system, includes a position determination system disposed between a blade and at least part of a hub. A grip couples the rotor blade to the hub. The position determination system comprises at least one magnet and a plurality of magnet sensors proximate to the at least one magnet.

Claims

1. A rotorcraft, comprising:

a body;

a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;

a hub coupled to the drive shaft;

a rotor blade;

a grip coupling the rotor blade to the hub; and

a position determination system disposed between the rotor blade and the body, the position determination system configured to measure a flapping of the rotor blade, the flapping of the rotor blade representing a vertical displacement of the rotor blade during operation, the position determination system comprising;

at least one magnet;

a plurality of magnet sensors proximate to the at least one magnet;

wherein the grip is positioned around a portion of the hub;

the grip has a closed end and an open end; and

the position determination system is disposed between the closed end of the grip and the at least part of the hub.

2. The rotorcraft of claim 1, wherein the plurality of magnet sensors comprise a plurality of Hall-effect sensors.

3. The rotorcraft of claim 1, wherein the position determination system comprises at least two magnets.

4. The rotorcraft of claim 1, wherein the position determination system is disposed between the rotor blade and at least part of a hub, wherein a grip couples the rotor blade to the hub.

5. The rotorcraft of claim 1, wherein the position determination system is disposed between the grip and at least part of the hub.

6. The rotorcraft of claim 1, wherein the position determination system is disposed between a rotor system and a rotor mast.

7. The rotorcraft of claim 1, wherein the position determination system is configured to determine the movement of the rotor blade in six dimensions as a function of relative location of the magnets to the sensors.

8. The rotorcraft of claim 1, wherein the at least one magnet is operable to produce a first magnetic field and a second magnetic field detectable by the plurality of magnet sensors.

9. The rotorcraft of claim 8, wherein the first magnetic field corresponds with a north pole of the at least one magnet and the second magnetic field corresponds with a south pole of the at least one magnet.

10. The rotorcraft of claim 1, wherein each of the plurality of magnet sensors is operable to:

receive an input voltage;

detect at least one magnetic field from the at least one magnet; and

vary an output voltage in response to the detected at least one magnetic field.

11. The rotorcraft of claim 10, wherein:

the at least one magnet is operable to produce a first magnetic field and a second magnetic field;

each of the plurality of magnet sensors is operable to increase the output voltage in response to detecting the first magnetic field; and

each of the plurality of magnet sensors is operable to decrease the output voltage in response to detecting the second magnetic field.

12. The rotorcraft of claim 1, further comprising a position determining unit in communication with the plurality of magnet sensors, the position determining unit operable to:

receive a plurality of voltage measurements from the plurality of magnet sensors; and

determine a position of the at least one magnet based on the received plurality of voltage measurements.

13. The rotorcraft of claim 12, the position determining unit further operable to determine a position of the rotor blade based on the position of the at least one magnet.

14. The rotorcraft of claim 12, the position determining unit operable to determine the position of the at least one magnet by comparing the plurality of voltage measurements received from the plurality of magnet sensors to a plurality of voltage records, each voltage record identifying:

a recorded position of the at least one magnet; and

a plurality of voltage values corresponding to the recorded position of the at least one magnet.

15. The rotorcraft of claim 14, wherein the plurality of voltage values of each voltage record represent values of the plurality of voltage measurements from the plurality of magnet sensors if the at least one magnet is located at the recorded position of the corresponding voltage record.

16. The rotorcraft of claim 12, the position determining unit operable to determine a position of the rotor blade by determining the position according to an Artificial Neural Network (ANN) model of the plurality of records.

17. The rotorcraft of claim 16, wherein the ANN model comprises one or more equations that express at least some of the travel range of the at least one topography generator based on the plurality of records.